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  • 1
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    Development of a real-time aeroperformance analysis technique for the X-29A advanced technical demonstrator (1990)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Aircraft (ISSN 0021-8669); 27; 660-667
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Flight tests confirm X-29 technologies (1989)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Results of test flights of the X-29A which confirmed the viability of the aircraft design and obtained good agreement with preflight predictions are presented. In addition to a forward-swept wing, the features to be evaluated on the X-29 demonstrator were: a digital fly-by-wire flight control, a close-coupled wing-canard configuration, an aeroelastically tailored composite wing skin and a three-surface pitch control configuration. The X-29A advanced technology demonstrator is a single-seat, fighter-type aircraft, best known for its forward-swept wing with a thin supercritical airfoil. The key objectives in developing the technologies incorporated into the X-29A design included establishing new airframe-design freedoms and options, as well as demonstrating that adequate levels of dynamic stability can be achieved by controlling an unstable airframe with a close-coupled canard, symmetric flap, and strake-flap combination. The X-29A aircraft and its related systems performed well and are now in a flight research phase.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Exxon Air World; 41; 2, 19
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Real-time flight test analysis and display techniques for the X-29A aircraft (1989)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The X-29A advanced technology demonstrator flight envelope expansion program and the subsequent flight research phase gave impetus to the development of several innovative real-time analysis and display techniques. These new techniques produced significant improvements in flight test productivity, flight research capabilities, and flight safety. These techniques include real-time measurement and display of in-flight structural loads, dynamic structural mode frequency and damping, flight control system dynamic stability and control response, aeroperformance drag polars, and aircraft specific excess power. Several of these analysis techniques also provided for direct comparisons of flight-measured results with analytical predictions. The aeroperformance technique was made possible by the concurrent development of a new simplified in-flight net thrust computation method. To achieve these levels of on-line flight test analysis, integration of ground and airborne systems was required. The capability of NASA Ames Research Center, Dryden Flight Research Facility's Western Aeronautical Test Range was a key factor to enable implementation of these methods.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AGARD, Flight Test Techniques; 17 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Overview of advanced wing design (1981)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Examples of experiment theory correlation are presented to give an indication of the capabilities and limitations of wing design and analysis for transonic applications by potential flow theory. The examples include correlations of experimental pressure distributions with theoretical results from isolated wing codes and wing-body codes. Both conservative and non conservative differencing as well as body and boundary layer corrections are considered. A full potential isolated wing code correlates well with data from an isolated wing test but may give poor prediction of the aerodynamic characteristics of some wing-body configurations. Potential flow wing body codes were found to improve the correlation for the wing-body configurations considered.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Langley Research Center Advan. Aerodyn. and Active Controls; p 157-169
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Preliminary flight assessment of the X-29A advanced technology demonstrator (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Several new technologies integrated on the X-29A advanced technology demonstrator are being evaluated for the next generation of fighter aircraft. Some of the most noteworthy ones are the forward-swept wing, digital fly-by-wire flight control system, close-coupled wing-canard configuration, aeroelastically tailored composite wing skins, three-surface pitch control configuration, and a highly unstable airframe. The expansion of the aircraft 1-g and maneuver flight envelopes was recently completed over a two-year period in 84 flights. Overall flight results confirmed the viability of the aircraft design, and good agreement with preflight predictions was obtained. The individual technologies' operational workability and performance were confirmed. This paper deals with the flight test results and the preliminary evaluation of the X-29A design and technologies. A summary of the primary technical findings in structural static loads, structural dynamic characteristics, flight control system characteristics, aerodynamic stability and control, and aerodynamic performance is presented.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-100407 , H-1427 , NAS 1.15:100407 , AIAA PAPER 87-2949
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Flight test techniques for the X-29A aircraft (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The X-29A advanced technology demonstrator is a single-seat, single-engine aircraft with a forward-swept wing. The aircraft incorporates many advanced technologies being considered for this country's next generation of aircraft. This unusual aircraft configuration, which had never been flown before, required a precise approach to flight envelope expansion. This paper describes the real-time analysis methods and flight test techniques used during the envelope expansion of the x-29A aircraft, including new and innovative approaches.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-88289 , H-1401 , NAS 1.15:88289 , AIAA PAPER 87-0082
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Challenges in modeling the X-29 flight test performance (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Presented are methods, instrumentation, and difficulties associated with drag measurement of the X-29A aircraft. The initial performance objective of the X-29A program emphasized drag polar shapes rather than absolute drag levels. Priorities during the flight envelope expansion restricted the evaluation of aircraft performance. Changes in aircraft configuration, uncertainties in angle-of-attack calibration, and limitations in instrumentation complicated the analysis. Limited engine instrumentation with uncertainties in overall in-flight thrust accuracy made it difficult to obtain reliable values of coefficient of parasite drag. The aircraft was incapable of tracking the automatic camber control trim schedule for optimum wing flaperon deflection during typical dynamic performance maneuvers; this has also complicated the drag polar shape modeling. The X-29A was far enough off the schedule that the developed trim drag correction procedure has proven inadequate. However, good drag polar shapes have been developed throughout the flight envelope. Preliminary flight results have compared well with wind tunnel predictions. A more comprehensive analysis must be done to complete performance models. The detailed flight performance program with a calibrated engine will benefit from the experience gained during this preliminary performance phase.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-88282 , H-1395 , NAS 1.15:88282 , AIAA PAPER 87-0081
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Preliminary design of a family of close air support aircraft (1989)
    In:  CASI
    Details
    Publication Date: 2017-03-17
    Description: A family of three Close Air Support (CAS) aircraft is presented. These aircraft are designed with commonality as the main design objective to reduce the life cycle cost. The aircraft are low wing, twin-boom, pusher turbo-prop configurations. The amount of information displayed to the pilot was reduced to a minimum to greatly simplify the cockpit. The aircraft met the mission specifications and the performance and cost characteristics compared well with other CAS aircraft. The concept of a family of CAS aircraft seems viable after preliminary design.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: USRA, NASA(USRA University Advanced Design Program Fifth Annual Summer Conference; p 293-302
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Real-time in-flight engine performance and health monitoring techniques for flight research application (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Procedures for real time evaluation of the inflight health and performance of gas turbine engines and related systems were developed to enhance flight test safety and productivity. These techniques include the monitoring of the engine, the engine control system, thrust vectoring control system health, and the detection of engine stalls. Real time performance techniques were developed for the determination and display of inflight thrust and for aeroperformance drag polars. These new methods were successfully shown on various research aircraft at NASA-Dryden. The capability of NASA's Western Aeronautical Test Range and the advanced data acquisition systems were key factors for implementation and real time display of these methods.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-104239 , H-1750 , NAS 1.15:104239
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Preliminary flight-determined subsonic lift and drag characteristics of the X-29A forward-swept-wing airplane (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The X-29A subsonic lift and drag characteristics determined, met, or exceeded predictions, particularly with respect to the drag polar shapes. Induced drag levels were as great as 20 percent less than wind tunnel estimates, particularly at coefficients of lift above 0.8. Drag polar shape comparisons with other modern fighter aircraft showed the X-29A to have a better overall aircraft aerodynamic Oswald efficiency factor for the same aspect ratio. Two significant problems arose in the data reduction and analysis process. These included uncertainties in angle of attack upwash calibration and effects of maneuver dynamics on drag levels. The latter problem resulted from significantly improper control surface automatic camber control scheduling. Supersonic drag polar results were not obtained during this phase because of a lack of engine instrumentation to measure afterburner fuel flow.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-100409 , H-1431 , NAS 1.15:100409
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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